Duct assembly for a gas turbine engine

Abstract

A gas turbine engine duct assembly includes a composite duct body that includes at least one rim. A flanged bracket includes a radially extending portion that defines a flange. An axially extending portion has an inner duct rim recess for accepting a portion of the at least one rim. At least one attachment plate has a projection recess for accepting a projection on the flanged bracket and an outer rim recess for accepting a portion of the at least one rim.

What is claimed is: 
     
       1. A gas turbine engine duct assembly comprising:
 a composite duct body including at least one rim; 
 a flanged bracket includes a radially extending portion defining a flange and an axially extending portion having an inner duct rim recess for accepting a portion of the at least one rim; and 
 at least one attachment plate having a projection recess for accepting a projection on the flanged bracket and an outer rim recess for accepting a portion of the at least one rim, wherein the projection includes a first axially facing projection surface extending in a first plane perpendicular to a central longitudinal axis of the flanged bracket and a second axially facing projection surface extending in a second plane perpendicular to the central longitudinal axis of the flanged bracket and the projection includes a first axially facing projection surface extending in a first plane perpendicular to a central longitudinal axis of the flanged bracket and a second axially facing projection surface extending in a second plane perpendicular to the central longitudinal axis of the flanged bracket. 
 
     
     
       2. The assembly of  claim 1 , wherein the projection includes a radially outward facing projection surface having a constant radial dimension between the first axially facing projection surface and the second axially facing projection surface. 
     
     
       3. The assembly of  claim 1 , wherein an inner surface of the composite duct body at least partially defines a bypass flow path. 
     
     
       4. The assembly of  claim 1 , wherein the at least one rim includes a larger cross section than a body portion of the composite duct body. 
     
     
       5. The assembly of  claim 1 , wherein the at least one rim includes a cross section having a diameter greater than a thickness of a body portion of the composite duct body. 
     
     
       6. The assembly of  claim 1 , wherein the projection forms a continuous circumferential lip surrounding a perimeter of a radially outer surface of the axially extending portion. 
     
     
       7. The assembly of  claim 1 , wherein the at least one rim includes a plurality of structural layers and shaping material surrounding by continuous outer fibers. 
     
     
       8. An attachment device for a bypass duct in a gas turbine engine comprising:
 a flanged bracket including
 a radially extending portion at least partially defining a flange; 
 an axially extending portion extending from a radially inner edge of the radially extending portion having a duct recess for accepting a portion of a duct and a projection extending radially outward from a radially outer surface of the axially extending portion; and 
 at least one attachment plate including a projection recess for accepting the projection, the at least one attachment plate is axially offset from the radially extending portion, and a fastener opening extends through the projection recess and is aligned with a fastener opening in the projection. 
 
 
     
     
       9. The device of  claim 8 , further comprising a fastener extending through the fastener opening in the bracket recess and the fastener opening in the projection. 
     
     
       10. The device of  claim 8 , wherein the at least one attachment plate includes an outer duct recess for accepting a portion of the rim of the duct and the outer duct recess is at least partially axially aligned with the inner duct recess. 
     
     
       11. The device of  claim 8 , wherein the projection includes a first axially facing projection surface extending in a first plane perpendicular to a central longitudinal axis of the flanged bracket and a second axially facing projection surface extending in a second plane perpendicular to the central longitudinal axis of the flanged bracket. 
     
     
       12. The device of  claim 11 , wherein the projection recess includes a first axially facing recess surface in abutting contact with the first axially facing projection surface and a second axially facing recess surface in abutting contact with the second axially facing projection surface. 
     
     
       13. A method of assembling a gas turbine engine duct comprising the steps of:
 locating a first portion of a rim of a composite duct in an inner rim recess on an axially extending portion of a flanged bracket; and 
 locating at least one attachment plate adjacent the axially extending portion, wherein the at least one attachment plate includes an outer rim recess for accepting a second portion of the rim and a projection recess for accepting a projection extending radially outward from the axially extending portion; and 
 locating at least one fastener through the projection recess on the at least one attachment plate and the projection on the flanged bracket. 
 
     
     
       14. The method of  claim 13 , wherein the projection includes a first axially facing projection surface extending in a first plane perpendicular to a central longitudinal axis of the flanged bracket and a second axially facing projection surface extending in a second plane perpendicular to the central longitudinal axis of the flanged bracket. 
     
     
       15. The method of  claim 13 , wherein the projection recess includes a first axially facing recess surface in abutting contact with the first axially facing projection surface and a second axially facing recess surface in abutting contact with the second axially facing projection surface.